DE102007007929B3 - Infantry weapon system for fighting fixed targets by means of steerable grenades fired from launchers - Google Patents

Abstract

Use of a miniaturized steering electronics (14) for determining the course of a launched from an infantry launcher designed as a rifle grenade launcher (10), the rocket motor (15) is ignited via a firing pin of the launcher in conjunction with a Zielassistenten (4), from the target For the elevation and azimuth of the launcher and determined from the positions of the launcher-serving shooter and the target to be achieved the values for the nominal trajectory (x) of the small steering missile, wherein over the target assistants (41) before the launch of the small missile (10) the mentioned values in the steering electronics (14) of the small missile (10) are fed.

Description

The The invention relates to an infantry weapon system for fighting fixed targets using shells fired from launchers, in particular of so-called rifle grenades.

rifle grenades are considered over caliber Shooting missiles fired from an infantry rifle become. The opposite an infantry bullet only lets considerably larger bullet weight low initial speeds for the grenade too, so only Reaches of up to 250 m can be achieved. There are rifle grenades also as grenades to be fired from shot cups. This shot mug are (as in the case of Aufsteckgeschosses AG36) to a rapid-fire rifle mountable. In other versions (eg as a grenade pistol) the thrower is executed as a separate weapon. Though Such weapon systems have the advantage of low system weight and thus increased mobility however, much below the disadvantage of much larger dispersion in the target towards pipe weapon systems, the far wider ranges can serve.

to Magnification of the Range and the pace are so-called nachbeschleunigte projectiles become known, who own a rocket engine in the bullet tail, which is ignited after leaving the gun barrel and then the projectile, So the grenade continues to drive. In this way, range increases can be of more than 20%, but the target dispersion can not be reduced.

Here now uses the invention, whose mission is in such weapon systems at least to increase the accuracy, but if possible also their range.

outgoing from the now possible strong Miniaturization electronic component and assemblies and the Presence of so-called satellite-based global position systems (GPS), this object is achieved by the use of a miniaturized control electronics to determine the course of a launched from an infantry launcher, as a so-called rifle grenade trained small steering rocket solved, whose Rocket engine over a firing pin of the pitcher is ignited, in conjunction with A target assistant, which consists of the desired values for elevation and azimuth of the Throwers and from the positions of the shooter serving and of the target to be reached, the values for the nominal trajectory of the small-arm rocket Determines this all in such an order that over the Zielassistenten before the launch of the small steering rocket the mentioned Values in the control electronics of the small missile for the purpose of guiding the Small-power missile can be fed into the target.

According to the invention So is advantageously a small missile as formed from a shot cup to star tende rifle grenade and with a control elements influencing control electronics provided. The Actuators are in the form of a pivotally mounted nose of the missile of the small missile educated. Advantageously, between control electronics and Missile missile rocket engine arranged to be transported in the target system of action, wherein a rocket motor penetrating central gas pipe as a carrier for aerodynamic Stabilizing fins and for serves the triggerable by means of the firing pin of the thrower fuze.

Of the suitable for use in the weapon system according to the invention Small missile can a Cartesian or a uniaxial (roll) control enabling Training of control electronics and Luftruder have.

Of the also attachable to the rifle target assistant for use in the weapon system according to the invention according to the invention at least one from a Global Position System (GPS) controlled flight guidance processor, an optical rangefinder with a rifle scope, its own Position reference system, a processor for calculating the nominal trajectory between the launch and the destination, as well as a fold-out Display for displaying the setpoint and actual values (launcher azimuth and elevation) on.

It However, also the attitude reference system of the small missile itself used to set the outlet angles before starting. To do this the attitude angle from the rifle grenade in the launcher - z. B. over Blue-Tooth technology - over the Processor of the target assistant to be transferred to the display. Likewise could the target data (distance, azimuth) from external, z. B. from already as equipment of the Infantrymen carried along Binoculars with E-knife and direction finder, via a suitable interface be fed.

Of the with a firing pin to trigger the igniter of the small missile exhibiting throwers - one Infantry rifle - is with a trigger of the firing pin before feeding the position of Sagittarius and Target obstructing lock provided.

To fight a target, the soldier aims at the target with the rangefinder on the rifle. The target data for distance and azimuth are used in the target wizard for the calculation of a Target trajectory implemented and stored in the flight control processor of the small missile. The nominal start angles (azimuth, elevation) are shown in the display and compared continuously with the actual angles. The latter are permanently determined by the orientation of the gun mounted on the rifle by means of the position reference system. If the nominal and actual values match, the small missile can be fired. From the start of the small missile, the on-board flight guidance system takes over the steering and steering in order to comply with the geodetic defined target trajectory as accurately as possible.

As a result the training of the rifle grenade as a small missile in Connection with the use of the course-determining objective assistant across from the range of ballistic missiles So the combat distance, much increased, at the same time significantly increased Accuracy without significantly increasing the system weight. In addition, it is now also the fight hidden targets possible.

According to the DE 2 252 627 A Although a method for maintaining the target value of a characteristic of the trajectory of a missile has become known, in which at launch or at a certain time after the launch of the missile missile side, a characteristic influencing parameter, which is associated with its most unfavorable value a target value, measured and is implemented at a deviation from the worst value in a control signal by which a defined change in the aerodynamic and / or flight mechanical behavior of the missile is resolved to compensate for this deviation.

This However, the method only relates to a previously determined correction a least favorable value a parameter of the trajectory of an unguided missile, can So the solution contribute nothing to the above-mentioned task.

The Invention is described below with reference to a in the drawing more or described less schematically illustrated weapon system with a small steering rocket.

It demonstrate:

1 a trained as a rifle grenade small rocket,

2 the block diagram of the control electronics, and

3 a front view of the weapon system according to the invention.

An in 1 shown in section by means of an infantry rifle from a shot cup to launch small missile 10 comprises in a tubular shell 11 a centrally arranged active system 13 , which may be lethal and / or non-lethal, as well as the front side then provided with a power supply control electronics 14 as well as a rocket motor on the back 15 , which is centric of a Gasleitrohr 17 is interspersed. The one discharge nozzle 18 having gas guide tube 17 is and carries a stabilizer stabilizer 19 in the form of deployable fins or in the form of a ring guide with a diameter that of the tubular shell 11 equivalent. The gas pipe 17 is about the stabilizer stabilizer 19 extended and is at its end by means of a primer 25 closed, which by means of a firing pin of the thrower, not shown here - shot cup at the infantry rifle - can be triggered. The not shown, the small missile 10 receiving shot cup is at an infantry gun, also not shown, z. As the rifle G36, releasably attached. The diameter of the tubular shell 11 is for example 40 mm.

At the front of the control electronics 14 is a tiltable missile nose 20 articulated as the trajectory of the small missile 10 influencing air impeller acts and of actuators 22 around the longitudinal axis 23 of the small missile 10 according to the steering signals of the control electronics 14 can be tilted by small angle β.

The determination of the steering signals for the nominal trajectory on which the small missile 10 as accurately as possible to the desired destination is done by means of a target assistant 41 who like the shot cup 44 is detachably fastened to the infantry rifle, cf. 3 ,

The target assistant 41 includes a GPS system, an optical rangefinder with telescopic sight 43 , a position reference system, a processor for calculating the desired trajectory between each shooting site and destination and a fold-out display 42 for displaying the setpoints and actual values, namely launcher azimuth and elevation.

The small missile 10 is a complete, consisting of extremely miniturisierten individual components steering electronics associated, consisting of inertial platform (I-MU), Global Position System (GPS), Baro altimeter, geomagnetic sensor (optional) and computer processors. A two-layer control algorithm for the path control and attitude control in flight ensures that the small missile 10 as accurately as possible on the target trajectory is guided in the target.

2 shows the effect of the club facht shown control electronics 14 , An input circuit 30 serves to feed the over the in 3 displayed target assistants 41 determined control signals in the form of the controlled variable x. About a comparison unit 31 which is also that of a probe 34 - Delivered current position signals of small missile 10 be fed, these signals arrive via an amplifier 32 to the actuators 22 , which via the movable nose of the missile 20 the trajectory of the shot small missile 10 influence in the given way. In the comparison unit 31 becomes the manipulated variable w (desired trajectory) and the controlled variable x (trajectory) the manipulated variable y for the actuators 22 determined.

The thrower, not shown in the form of a shot with the said cup 44 and the destination assistant 41 Equipped infantry rifle is provided with a lock, not shown here, which prevents that before storing the controlled variable X in the control electronics 14 of the small missile 10 the primer 25 over the firing pin of the thrower can be released.

10

Small Missile

11

tubular shell

13

active system

14

control electronics

15

rocket engine

17

gas conduit pipe

18

exhaust nozzle

19

stabilizing fin

20

Missile nose

22

actuators

23

longitudinal axis

25

detonator

30

input circuit

31

comparing unit

32

amplifier

34

probe

41

target assistant

42

trundle display

43

rangefinder with rifle scope

44

shot cup

x

Controlled variable (actual trajectory)

y

manipulated variable

w

Reference variable (nominal trajectory)

Claims (6)

Procedure ( 14 ) determining the course of a small-bore missile launched as a rifle grenade from an infantry launcher ( 10 ), whose rocket engine ( 15 ) is fired via a firing pin of the thrower and its miniaturized control electronics ( 14 ) in conjunction with a target assistant ( 41 ), which determines from the target values for elevation and azimuth of the launcher and from the positions of the launcher serving the launcher and the target to be reached the values for the desired trajectory (w) of the small missile ( 10 ), all in such an order that the target assistant ( 41 ) before the launch of the small missile ( 10 ) the said values into the control electronics ( 14 ) of the small missile ( 10 ) for the purpose of guiding the small missile ( 10 ) are fed into the destination. Small missile ( 10 ) for use according to the features of claim 1, characterized in that as actuators of the control electronics ( 14 ) Luftruder in the form of a pivotally mounted missile nose ( 20 ) are provided. Small missile ( 10 ) according to claim 2, characterized by a between control electronics ( 14 ) and rocket motor ( 15 ) arranged active system ( 13 ) and by a rocket motor ( 15 ) centrally penetrating Gasleitrohr ( 17 ), which is used as a carrier for the aerodynamic stabilizer stabilizer ( 19 ) and for the triggerable by means of the firing pin of the thrower primer ( 25 ) serves. Small missile ( 10 ) according to claims 2 and 3, characterized by a Cartesian or a uniaxial (roll) control enabling training of control electronics ( 14 ) and missile nose ( 20 ). Target Assistant ( 41 ) for use according to the features of claim 1, characterized in that this target assistant ( 41 ) at least one Global Positioning System (GPS), a rangefinder with telescopic sight ( 43 ), a hinged display ( 42 ), an azimuth / elevation of the launcher determining position reference system, as well as a processor which for determining the target trajectory of the small missile missile compelling signals (x) comprises. Thrower for use according to the features of claim 1, with a firing pin for triggering the primer ( 25 ) of the small missile ( 10 ), characterized in that one of the triggering of the firing pin before feeding the controlled variable (x) for determining the desired trajectory of the small missile ( 10 ) has a blocking barrier.